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DOUGLAS LA203A AIRFOIL (la203a-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: DOUGLAS LA203A AIRFOIL (la203a-il)
Reynolds number: 500,000
Max Cl/Cd: 124.02 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-la203a-il-500000-n5.txt
Download as CSV file: xf-la203a-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: DOUGLAS LA203A AIRFOIL                          
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.0940   0.09718   0.09321  -0.0890   0.7219   0.0252
 -10.000  -0.0890   0.09374   0.08976  -0.0908   0.7186   0.0253
  -9.500  -0.3204   0.02818   0.02296  -0.1495   0.7147   0.0276
  -9.250  -0.3025   0.02568   0.02016  -0.1515   0.7116   0.0278
  -9.000  -0.2784   0.02465   0.01903  -0.1524   0.7084   0.0280
  -8.750  -0.2532   0.02387   0.01817  -0.1531   0.7053   0.0282
  -8.500  -0.2276   0.02314   0.01735  -0.1538   0.7024   0.0285
  -8.250  -0.2016   0.02236   0.01645  -0.1545   0.6998   0.0287
  -8.000  -0.1756   0.02147   0.01539  -0.1552   0.6971   0.0290
  -7.750  -0.1490   0.02045   0.01423  -0.1560   0.6944   0.0293
  -7.500  -0.1220   0.01949   0.01312  -0.1567   0.6915   0.0296
  -7.250  -0.0946   0.01860   0.01208  -0.1574   0.6887   0.0299
  -7.000  -0.0669   0.01780   0.01113  -0.1580   0.6861   0.0303
  -6.750  -0.0389   0.01709   0.01027  -0.1585   0.6835   0.0307
  -6.500  -0.0107   0.01647   0.00950  -0.1590   0.6810   0.0310
  -6.250   0.0179   0.01589   0.00883  -0.1594   0.6784   0.0314
  -6.000   0.0466   0.01540   0.00825  -0.1599   0.6755   0.0317
  -5.750   0.0753   0.01485   0.00766  -0.1603   0.6728   0.0320
  -5.500   0.1042   0.01447   0.00726  -0.1608   0.6700   0.0324
  -5.250   0.1331   0.01416   0.00693  -0.1612   0.6672   0.0328
  -5.000   0.1622   0.01389   0.00660  -0.1616   0.6646   0.0332
  -4.750   0.1915   0.01360   0.00631  -0.1620   0.6619   0.0338
  -4.500   0.2210   0.01333   0.00602  -0.1624   0.6592   0.0344
  -4.250   0.2504   0.01306   0.00571  -0.1628   0.6562   0.0351
  -4.000   0.2799   0.01280   0.00540  -0.1632   0.6532   0.0357
  -3.750   0.3094   0.01255   0.00511  -0.1636   0.6503   0.0362
  -3.500   0.3392   0.01226   0.00481  -0.1642   0.6477   0.0368
  -3.250   0.3692   0.01205   0.00462  -0.1647   0.6449   0.0375
  -3.000   0.3993   0.01186   0.00444  -0.1652   0.6417   0.0383
  -2.750   0.4293   0.01168   0.00426  -0.1657   0.6384   0.0391
  -2.500   0.4593   0.01152   0.00408  -0.1662   0.6352   0.0401
  -2.250   0.4892   0.01140   0.00391  -0.1666   0.6322   0.0410
  -2.000   0.5196   0.01124   0.00376  -0.1673   0.6292   0.0423
  -1.750   0.5500   0.01111   0.00367  -0.1678   0.6260   0.0437
  -1.500   0.5802   0.01100   0.00356  -0.1683   0.6226   0.0452
  -1.250   0.6105   0.01091   0.00346  -0.1688   0.6190   0.0465
  -1.000   0.6408   0.01080   0.00336  -0.1694   0.6156   0.0484
  -0.750   0.6708   0.01075   0.00329  -0.1698   0.6126   0.0507
  -0.500   0.7013   0.01067   0.00324  -0.1704   0.6092   0.0538
  -0.250   0.7315   0.01060   0.00320  -0.1709   0.6054   0.0578
   0.000   0.7616   0.01055   0.00318  -0.1714   0.6016   0.0632
   0.250   0.7916   0.01052   0.00316  -0.1719   0.5979   0.0723
   0.500   0.8217   0.01049   0.00315  -0.1724   0.5945   0.0869
   0.750   0.8530   0.01036   0.00317  -0.1732   0.5908   0.1241
   1.000   0.8968   0.00945   0.00326  -0.1778   0.5866   0.5038
   1.250   0.9278   0.00941   0.00340  -0.1785   0.5825   0.5859
   1.500   0.9571   0.00948   0.00350  -0.1787   0.5787   0.6223
   1.750   0.9864   0.00954   0.00362  -0.1790   0.5751   0.6445
   2.000   1.0154   0.00961   0.00372  -0.1791   0.5707   0.6623
   2.250   1.0440   0.00970   0.00382  -0.1792   0.5664   0.6778
   2.500   1.0723   0.00980   0.00392  -0.1793   0.5625   0.6871
   2.750   1.1008   0.00990   0.00402  -0.1794   0.5588   0.6939
   3.250   1.1575   0.01008   0.00423  -0.1796   0.5497   0.7040
   3.500   1.1853   0.01020   0.00434  -0.1795   0.5452   0.7104
   3.750   1.2133   0.01033   0.00447  -0.1796   0.5413   0.7174
   4.000   1.2413   0.01042   0.00461  -0.1796   0.5369   0.7229
   4.250   1.2688   0.01055   0.00475  -0.1796   0.5319   0.7285
   4.500   1.2958   0.01071   0.00489  -0.1795   0.5270   0.7342
   4.750   1.3233   0.01083   0.00505  -0.1795   0.5222   0.7394
   5.000   1.3504   0.01096   0.00522  -0.1793   0.5165   0.7449
   5.250   1.3764   0.01115   0.00540  -0.1790   0.5102   0.7515
   5.500   1.4027   0.01131   0.00558  -0.1788   0.5028   0.7580
   5.750   1.4273   0.01152   0.00579  -0.1783   0.4930   0.7645
   6.000   1.4520   0.01174   0.00601  -0.1777   0.4814   0.7716
   6.250   1.4748   0.01203   0.00627  -0.1769   0.4671   0.7784
   6.500   1.4961   0.01238   0.00657  -0.1758   0.4504   0.7862
   7.000   1.5351   0.01323   0.00731  -0.1731   0.4145   0.8038
   7.500   1.5696   0.01421   0.00821  -0.1696   0.3809   0.8232
   7.750   1.5830   0.01476   0.00873  -0.1672   0.3644   0.8342
   8.000   1.5937   0.01539   0.00933  -0.1644   0.3470   0.8477
   8.250   1.6026   0.01613   0.01004  -0.1614   0.3287   0.8635
   8.500   1.6084   0.01702   0.01089  -0.1581   0.3088   0.8826
   8.750   1.6086   0.01810   0.01194  -0.1540   0.2876   0.9112
   9.000   1.6011   0.01930   0.01310  -0.1488   0.2676   0.9999
   9.250   1.6021   0.02109   0.01477  -0.1461   0.2425   0.9999
   9.500   1.6019   0.02312   0.01668  -0.1435   0.2195   0.9999
   9.750   1.6024   0.02521   0.01868  -0.1413   0.1982   0.9999
  10.000   1.6030   0.02736   0.02075  -0.1392   0.1791   0.9999
  10.250   1.6040   0.02953   0.02285  -0.1372   0.1626   0.9999
  10.500   1.6047   0.03174   0.02500  -0.1353   0.1477   0.9999
  10.750   1.6055   0.03396   0.02718  -0.1334   0.1340   0.9999
  11.000   1.6056   0.03627   0.02944  -0.1316   0.1214   0.9999
  11.250   1.6051   0.03867   0.03180  -0.1298   0.1094   0.9999
  11.500   1.6052   0.04107   0.03417  -0.1282   0.0990   0.9999
  11.750   1.6057   0.04347   0.03654  -0.1266   0.0898   0.9999
  12.000   1.6065   0.04591   0.03896  -0.1252   0.0820   0.9999
  12.250   1.6087   0.04827   0.04132  -0.1240   0.0751   0.9999
  12.500   1.6117   0.05058   0.04364  -0.1228   0.0696   0.9999
  12.750   1.6132   0.05310   0.04616  -0.1216   0.0646   0.9999
  13.000   1.6176   0.05534   0.04843  -0.1206   0.0605   0.9999
  13.250   1.6196   0.05790   0.05100  -0.1197   0.0569   0.9999
  13.500   1.6241   0.06019   0.05334  -0.1188   0.0539   0.9999
  13.750   1.6267   0.06273   0.05591  -0.1179   0.0511   0.9999
  14.000   1.6298   0.06522   0.05843  -0.1171   0.0488   0.9999
  14.250   1.6329   0.06777   0.06103  -0.1164   0.0466   0.9999
  14.500   1.6356   0.07036   0.06365  -0.1157   0.0445   0.9999
  14.750   1.6375   0.07309   0.06643  -0.1151   0.0429   0.9999
  15.000   1.6409   0.07563   0.06902  -0.1145   0.0412   0.9999
  15.250   1.6425   0.07842   0.07187  -0.1140   0.0397   0.9999
  15.500   1.6439   0.08126   0.07474  -0.1135   0.0383   0.9999
  15.750   1.6456   0.08410   0.07764  -0.1131   0.0371   0.9999
  16.000   1.6479   0.08687   0.08047  -0.1127   0.0360   0.9999
  16.250   1.6492   0.08978   0.08344  -0.1124   0.0349   0.9999
  16.500   1.6494   0.09282   0.08654  -0.1122   0.0338   0.9999
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